Design.Analyze.Validate.

HART-120 Flexible High-Aspect-Ratio Wing

Original fictional transport-wing study built around a real aerospace systems problem: higher aspect ratio reduces induced drag but increases structural mass, flexibility and gust/maneuver loads. I coupled reduced-order aerodynamics, beam/wingbox sizing, passive aeroelastic redistribution, active load alleviation, fail-safe sizing, mission analysis, ML surrogates and Monte Carlo robustness verification.

Engineering conclusion: the final AR 15.5 concept closes the project-level structural, mission and robustness gates only after fail-safe structure, technology-system mass and uncertainty are included. ML accelerates screening; finalists are returned to the transient physics model for verification.

FLEX-445 Hybrid Flutter Mitigation

Public-benchmark aeroelastic design study based on AGARD 445.6. I built a four-mode DLM/p-k model, validated it against published flutter data, investigated passive torsional tailoring and finite-bandwidth/delay active control, then used physics-generated ML surrogates to screen 100,000 hybrid architectures before returning shortlisted designs to the original solver.

Engineering conclusion: within the reduced-order design space, the physics-verified minimum-authority hybrid candidate met the flutter and fail-safe targets with roughly one-quarter of the robust active-only authority. Five ML candidates were re-run through the physics model; only three passed every final requirement.

NACA0012 Control-Surface Hinge

Control-surface hinge design study linking a public NACA0012 reference section to MATLAB load screening and analytical sizing, SolidWorks CAD, local contact FEA and analytical-to-FEA correlation. The hinge is placed at 75% chord and sized around a 322.33 N design reaction.

Engineering conclusion: the local FEA peak is 1.65× the nominal analytical pin stress because the finite-element model resolves contact, bearing and geometric stress concentration that the hand calculation intentionally smooths out.

AeroStruct-15MW

Independent reduced-order study built around the public IEA 15-MW reference turbine. I developed and validated a BEM aerodynamic model, coupled it to rotating-beam structural analysis, generated a physics design database, trained ML surrogates, searched 100,000 candidate designs and re-verified the Pareto-selected solutions with the physics model.

Engineering conclusion: within the bounded reduced-order design space, the optimum moved toward smooth outboard aerodynamic load redistribution rather than additional structural material. Results are physics-verified within the model assumptions, not IEC/OpenFAST certification claims.

Adjustable Lifting Fixture

End-to-end concept design for a 300 kg eccentric load. Reactions, beam sizing, pin/lug failure modes and connection geometry were calculated before CAD, followed by a preliminary SolidWorks static FEA.

Multi-Element WingSail CFD

MSc thesis study of a NACA 0018-based rigid wingsail with hinged-flap and gap configurations. The OpenFOAM workflow examined flap deflection, hinge position, gap size and operating orientation, including thrust and side-force decomposition.

Cantilever Beam Design Analyzer

A structural analysis tool that separates strength from serviceability, calculates allowable loads, analytically resizes the section and checks the redesign with a 50-point parametric study.